CN113027815B - Impeller comprising partial stepped blades and design method thereof - Google Patents
Impeller comprising partial stepped blades and design method thereof Download PDFInfo
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- CN113027815B CN113027815B CN202110339895.1A CN202110339895A CN113027815B CN 113027815 B CN113027815 B CN 113027815B CN 202110339895 A CN202110339895 A CN 202110339895A CN 113027815 B CN113027815 B CN 113027815B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/281—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for fans or blowers
- F04D29/282—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for fans or blowers the leading edge of each vane being substantially parallel to the rotation axis
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/30—Vanes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/667—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by influencing the flow pattern, e.g. suppression of turbulence
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/20—Hydro energy
Abstract
The invention relates to an impeller comprising local step-shaped blades and a design method thereof, wherein boundary layer separation of air flow is continuously developed and deteriorated along with the increase of diameter in a closed impeller flow channel of a centrifugal fan in a backward centrifugal fan closed impeller widely applied at present, and on the premise that the angle of a blade inlet and a blade outlet, the diameter of the inlet and the outlet, the number of the blades and the width of a blade channel inlet are not changed, a series of local micro steps are arranged at the peripheral part of the blade, so that the degree of boundary layer separation of She Daona and the sustainable development and the loss caused by the degree are tried to be weakened, the efficiency of the impeller to work on air is improved, the aerodynamic performance and the efficiency of the impeller and the fan are improved, and the main structural size and the inlet and outlet mounting angle of the impeller are kept unchanged.
Description
Technical Field
The invention relates to the technical field of ventilators, in particular to an impeller comprising partial stepped blades and a design method thereof.
Background
In general, most of the impellers of the backward centrifugal ventilator are closed impellers, and mainly comprise a rear disc 3, a front disc 2 and a plurality of blades 1 arranged between the rear disc and the front disc, wherein an inner hole of the front disc is an impeller inlet, as shown in fig. 1. The blade flow channel of the closed impeller is a channel surrounded by adjacent blades and the front impeller disk and the rear impeller disk. The inlet width of the vane channel is an important structural parameter, which is the width of the flow channel on the inlet side of the vane. The diameter of the inlet and outlet of the blade, the shape of the blade, the installation position and the number of the blades determine the shape of the blade path, the shape of the blade path is good or bad, the severity of boundary layer separation on the surface of the blade is determined, and the working efficiency and the working capacity of the impeller are greatly influenced.
In a closed centrifugal impeller, since the number of blades is not infinite but a certain number of limited blades, the circumferential velocity distribution on the cross section of the blade path is uneven, and the uneven circumferential velocity distribution is caused by axial vortex of the rotation She Daona, so that the theoretical pressure of the impeller when the number of blades is limited is necessarily smaller than the theoretical pressure when the number of blades is infinite, and the ratio of the former to the latter is a circulation coefficient or a slip coefficient. Since the gas medium has viscosity, a boundary layer is generated in the flow in the vane path, and the thickness thereof is small, but the influence on the flowing state is great, and the friction force generated in the flowing of the gas is generated in the boundary layer. The existence of the boundary layer reduces the effective through-flow sectional area of the vane channel, so that the speed of the main air flow is slightly increased, interference is formed on the main air flow, more importantly, viscosity and the sustainable development of the boundary layer can occur at the position close to the wall surface, and backflow can occur to separate the boundary layer from the wall surface, so that a certain vortex is formed, and larger loss is caused. The interference of the boundary layer to the main air flow and the boundary layer separation form larger loss, and the work efficiency and the work capacity of the impeller to the air are reduced.
Disclosure of Invention
In the closed impeller of the backward centrifugal ventilator widely applied at present, a series of local micro steps are arranged at the peripheral part of the blades, so that the separation degree of a boundary layer of She Daona and the continuous development degree and the loss caused by the separation degree are reduced, the efficiency of the impeller on gas acting is improved, the aerodynamic performance and the efficiency of the impeller and the ventilator are improved, and the main structural size and the inlet and outlet mounting angle of the impeller are kept unchanged.
The invention realizes the above purpose through the following technical scheme: an impeller comprising partially stepped blades, the impeller comprising a plurality of arc-shaped backward blades, the working face of the blades comprising a smooth section and a stepped section; the step section is close to the outer edge of the blade; the inner edge of the step section is as follows: the center of the impeller is taken as the center of a circle, and the diameter is phi D n Is a circular arc section of the ring; the step section comprises n continuous gradually outwards convex steps.
Further, the width of the inlet of the runner of the adjacent blade is W, the diameters of the inlet and outlet of the arc of the working surface of the blade are respectively corresponding to the point c and the point a of the bus of the blade, W is the minimum distance from the point c to the non-working surface of the adjacent other blade, the point c ' of the non-working surface is corresponding to the point c ', and the intersection point of the cc ' extension line and the working surface of the blade is the point c ' '; taking the connecting line of the point c' and the center of the impeller as a radius to form a first circle, wherein the diameter of the first circle is phi D W The method comprises the steps of carrying out a first treatment on the surface of the The phi D n =（1.015～1.045）×ΦD w 。
Further, the step has a ramp height less than the vane thickness.
Further, the blade outlet diameter is phi D 2 The stage is located at the diameter phi D n And phi D 2 Between them.
The application also providesA design method of an impeller comprising partial step-shaped blades comprises a plurality of uniformly distributed arc-shaped backward blades, wherein the diameters of the inlet and outlet of the blades are phi D respectively 1 And phi D 2 The end points of the blade bus are the point c and the point a, and the blade wrap angle is phi;
the width of the runner inlet of the adjacent blade is W, W is the minimum distance from the point c to the non-working surface of the adjacent blade, the point c ' of the non-working surface of the adjacent blade corresponds to the point c ' of the extension line cc ' and the intersection point of the working surface of the blade is the point c ' ';
the design method comprises the following steps:
1) Taking the connecting line of the point c' and the center of the impeller as a radius to form a first circle, wherein the diameter of the first circle is phi D W The method comprises the steps of carrying out a first treatment on the surface of the Taking the center of the impeller as a round point, and the diameter of the round point along the arc line of the blade is smaller than phi D W Is an inner arc, greater than phi D W The part of the arc line is an outer end arc line;
2) Selecting diameter phi D n ，ΦD n =（1.015～1.045）×ΦD w ；
3) Diameter phi D along the radial direction of the impeller n And phi D 2 The outer end arc line of the blade between the blades is divided into n sections of arc lines;
4) And (3) taking the center of the impeller as the center, respectively rotating the n arc lines outwards at a certain rotation angle, and sequentially connecting adjacent arc lines obtained after rotation, so that a series of tiny steps are formed on the surface of the blade.
Further, the diameter phi D of the blade bus n The corresponding point is a n The dividing mode is as follows: d (D) i =D 2 -(D 2 -D n ) X i/n, where i= [1, n]，n=[3,20]From diameter phiD 2 To phi D n The intersection points of each concentric circle and the blade bus are as follows in sequence: a, a 1 ,…，a i ,…，a (n-1) ,a n I.e. from point a to point a on the blade outer end bus n The bus segments of the dots are divided into: aa 1 ,a 1 a 2 ,…，a (i-1) a i ，…，a (n-1) a n N segments in total.
Further, the method comprises the steps of,aa of the 1 ,a 1 a 2 ,…，a (i-1) a i ，…，a (n-1) a n Respectively rotates to a new position aa 1 Rotated to bb 1 ，a 1 a 2 Rotated to c 1 b 2 ,…，a (i-1) a i Rotated to c (i-1) b i ，…，a (n-1) a n Rotated to c (n-1) b n ；a (n-1) a n The rotation angle of the segment is theta n =θ，a (n-2) a (n-1) The rotation angle of the segment is theta (n-1) =2×θ，…，a (i-1) a i The rotation angle of the segment is theta i =(n-i+1) ×θ，…， a 1 a 2 The rotation angle of the segment is theta 2 = (n-1)×θ，aa 1 The rotation angle of the segment is theta 1 =n×θ; through the respective rotation of the arc sections, the wrap angle phi of the blade is reduced to phi 1 ，φ 1 =φ-n×θ。
Further, the adjacent arc lines obtained after rotation are sequentially connected in the following connection mode: straight line connection c i Point and b i Point, i= [1, n]Passing through the middle point e i Line segment c i b i Is a perpendicular f to i g i And arc line section c (i-1) b i Intersecting at f i And arc line section c i b (i+1) Intersecting at g i In e i The point is taken as the center, and the straight line f i g i Rotated by an angle gamma in the opposite direction to the direction of rotation of the impeller, wherein gamma= [5 °,40 ]]With blade arc segment c (i-1) b i Intersecting at u i With blade arc segment c i b (i+1) Intersecting at v i ，γ=[5°，40°]Thereby forming u 1 v 1 ，u 2 v 2 ，…，u i v i ，…，u n v n N partial step shapes in total.
Further, a compound arc "bu" comprising n partial step shapes 1 v 1 u 2 v 2 …u i v i …u n v n c' cambered surface as blade working surfaceA wire.
Further, θ= [0.05 °,0.25 ° ].
Further, the step has a ramp height less than the vane thickness.
Compared with the prior art, the invention has the following beneficial effects: in a closed impeller flow passage of a centrifugal fan, boundary layer separation of air flow is continuously developed and deteriorated along with the increase of the diameter, and on the premise that the angle of a blade inlet and a blade outlet, the diameter of the inlet and the outlet, the number of the blades and the width of a blade passage inlet are not changed, a series of local micro steps are additionally arranged on a blade outlet section, so that the continuous development and deterioration of the boundary layer separation are restrained to a certain extent, the reduction of the area of a main air flow passage and the larger loss caused by the boundary layer separation are reduced, and the working capacity and the working efficiency of the impeller can be improved to a certain extent.
Drawings
FIG. 1 is a schematic cross-sectional view of an impeller;
FIG. 2 is a schematic perspective view of an impeller of the present application;
FIG. 3 is a view of the circumferential surface of an impeller blade;
FIG. 4 is an out-of-blade Zhou Huxian sectional view;
FIG. 5 is a schematic illustration of deflection after aliquoting the blade outer Zhou Huxian;
FIG. 6 is an enlarged view of section I of FIG. 5;
FIG. 7 is an enlarged view of portion II of FIG. 6;
FIG. 8 is a step-like formation process diagram of the peripheral blade;
FIG. 9 is a diagram of an outer Zhou Shepian step formation process II;
FIG. 10 is a third step-like formation process of the peripheral blade;
fig. 11 is a diagram of an outer Zhou Shepian step formation process fourth;
FIG. 12 is an enlarged view of the portion III of FIG. 11;
FIG. 13 is a schematic perspective view of a blade;
FIG. 14 is a graph of static pressure versus comparative prototype one of example one;
FIG. 15 is a graph of static pressure efficiency versus sample machine I;
FIG. 16 is a graph of static pressure versus sample machine two for example two;
FIG. 17 is a graph comparing static pressure efficiency for example two with sample comparison machine two;
FIG. 18 is a graph of static pressure versus comparative prototype III of example III;
FIG. 19 is a graph of static pressure efficiency versus sample machine III.
Description of the embodiments
The invention is further described below with reference to the accompanying drawings:
an impeller comprising partially stepped blades, the impeller comprising 7 arcuate backward blades, the working face of the blades comprising smooth sections and stepped sections, the stepped sections being adjacent the outer edges of the blades. The inner edges of the stage are: the center of the impeller is taken as the center of a circle, and the diameter is phi D n Is a circular arc section of the ring; the step section comprises n continuous steps which gradually protrude outwards. The width of the runner inlet of the adjacent blade is W, the diameters of the inlet and outlet of the arc of the working surface of the blade correspond to the point c and the point a of the blade bus respectively, W is the minimum distance from the point c to the non-working surface of the adjacent other blade, the point c ' of the non-working surface corresponds to the point c ' of the non-working surface, and the intersection point of the cc ' extension line and the working surface of the blade is the point c ' '; taking the connecting line of the point c' and the center of the impeller as a radius to form a first circle, wherein the diameter of the first circle is phi D W ；ΦD n =（1.015～1.045）×ΦD w 。
Blade outlet diameter phiD 2 The stage being located at diameter phiD n And phi D 2 Between them.
As shown in FIG. 2, the inlet and outlet diameters of the blades are phi D respectively 1 And phi D 2 I.e. the length of the impeller reaching the inlet of the working surface of the blade is D by taking the center of the impeller as the circle center o 1 2, the length of the blade reaching the outlet of the working surface of the blade is D 2 And 2, the endpoints of the blade bus are the point c and the point a, the wrap angle of the blade is phi, namely the included angle between oc and oa is phi.
The width of the runner inlet of the adjacent blade is W, W is the minimum distance from the point c to the non-working surface of the adjacent blade, the point c 'of the non-working surface of the corresponding adjacent blade, and the intersection point of the cc' extension line and the working surface of the blade is the point c ''.
The design method of the impeller with the partial stepped blades comprises the following steps:
1) Taking the connecting line of the point c' and the center of the impeller as a radius to form a first circle, wherein the diameter of the first circle is phi D W The method comprises the steps of carrying out a first treatment on the surface of the The center of the impeller is taken as a round point, and the diameter of the impeller along the arc line of the impeller is smaller than phi D W Is an inner arc, greater than phi D W Is the outer arc.
2) Selecting diameter phi D n ，ΦD n =（1.015～1.045）×ΦD w 。
3) Diameter phi D along the radial direction of the impeller n And phi D 2 The outer end arc of the blade between the two is divided into n sections of arc lines, as shown in figure 3.
The diameter phi D is selected n And phi D 2 The outer end arc line of each blade is divided into n sections of arc lines because W is the width of the inlet of the flow channel between the adjacent blades, the size of the arc lines has larger influence on the flowing state in the blade channel, and the diameter phi Dn of the initial position of the step section is larger than the diameter phi D corresponding to the inlet width W W It is ensured that the inlet width W does not change due to the segmentation of the vane outer Zhou Huxian and its deflection.
Diameter phi D on blade bus n The corresponding point is a n The dividing mode is as follows: d (D) i =D 2 -(D 2 -D n ) X i/n, where i= [1, n]，n=[3,20]From diameter phiD 2 To phi D n The intersection points of each concentric circle and the blade bus are as follows in sequence: a, a 1 ,…，a i ,…，a (n-1) ,a n I.e. from point a to point a on the blade outer end bus n The bus segments of the dots are divided into: aa 1 ,a 1 a 2 ,…，a (i-1) a i ，…，a (n-1) a n N segments in total.
4) The center of the impeller is taken as the center, n sections of arc lines are respectively rotated outwards at a certain rotation angle, and adjacent arc line sections obtained after rotation are sequentially connected, so that a series of steps are formed on the surface of the blade.
As shown in FIGS. 4-6, aa 1 ,a 1 a 2 ,…，a (i-1) a i ，…，a (n-1) a n Respectively rotates to a new position aa 1 Rotated to bb 1 ，a 1 a 2 Rotated to c 1 b 2 ,…，a (i-1) a i Rotated to c (i-1) b i ，…，a (n-1) a n Rotated to c (n-1) b n ；a (n-1) a n The rotation angle of the segment is theta n =θ，a (n-2) a (n-1) The rotation angle of the segment is theta (n-1) =2×θ，…，θ i =a (i-1) a i The rotation angle of the segment is theta i =(n-i+1) ×θ，…， a 1 a 2 The rotation angle of the segment is theta 2 = (n-1)×θ，aa 1 The rotation angle of the segment is theta 1 =n×θ; through the respective rotation of the arc sections, the wrap angle phi of the blade is reduced to phi 1 ，φ 1 =Φ -n×θ. Wherein θ= [0.05 °,0.25 ]]Because the value of theta is smaller and the number of n is limited, the value of the wrap angle of the blade is not obvious, and the installation angle of the outlet is unchanged after the outermost arc line is rotated.
As shown in fig. 7-13, adjacent arc segments obtained after rotation are connected in sequence in the following connection manner: straight line connection c i Point and b i Point, i= [1, n]Passing through the middle point e i Line segment c i b i Is a perpendicular f to i g i And arc line section c (i-1) b i Intersecting at f i And arc line section c i b (i+1) Intersecting at g i In e i The point is taken as the center, and the straight line f i g i Rotated by an angle gamma in the opposite direction to the direction of rotation of the impeller, wherein gamma= [5 °,40 ]]With blade arc segment c (i-1) b i Intersecting at u i With blade arc segment c i b (i+1) Intersecting at v i Thereby forming u 1 v 1 ，u 2 v 2 ，…，u i v i ，…，u n v n N partial step shapes in total, a composite arc line 'bu' comprising n partial step shapes 1 v 1 u 2 v 2 …u i v i …u n v n c' as a vane workAnd (5) forming an arc-shaped line of the surface. Wherein the height of the step inclined plane is smaller than the thickness of the blade plate, namely: delta i ＜t。
The improvement scheme of the patent does not change the main structural size and the inlet and outlet installation angle of the impeller, and the curvature of each arc segment of the blade is also unchanged. The series of local steps of the blade working surface weakens the boundary layer separation of She Daona and the continuous development degree and the loss caused by the boundary layer separation to a certain extent, so that the efficiency of the impeller on the working of the gas is improved, and the aerodynamic performance and the efficiency of the ventilator are further improved.
Three sets of examples are set forth below to demonstrate the effect of the improved impeller on the static pressure and static pressure efficiency of the ventilator.
TABLE 1
Examples
The first embodiment is formed by arranging the step improvement on the periphery of the blade on the basis of the first comparison model, other main dimensions of the impeller and the ventilator are consistent with those of the first comparison model, and relevant dimensions are shown in table 1.
The performance curves of example one and comparative prototype one are compared to fig. 14-15; the comparison of the performance parameters of the same air quantity working point is shown in table 2.
TABLE 2
Under the working condition of the same air quantity, compared with the comparative sample machine I, the static pressure of the embodiment I is improved by 49Pa, and the static pressure efficiency is improved by 1.19%.
Examples
In the second embodiment, the step-shaped improvement of the periphery of the blade is arranged on the basis of the second comparison model machine, and other main dimensions of the impeller and the ventilator are consistent with those of the second comparison model machine. The relevant dimensions are shown in table 1.
The comparison of the performance curves of the second example and the second comparative prototype is shown in fig. 16-17; the comparison of the performance parameters of the same air quantity working point is shown in table 3.
TABLE 3 Table 3
Under the working condition of the same air quantity, compared with a comparative sample machine II, the static pressure of the embodiment II is improved by 24Pa, and the static pressure efficiency is improved by 1.2%.
Examples
In the third embodiment, the step-shaped improvement of the periphery of the blade is arranged on the basis of the third comparison model machine, and other main dimensions of the impeller and the ventilator are consistent with those of the third comparison model machine. The relevant dimensions are shown in table 1.
The performance curves of example III and comparative prototype III are compared in FIGS. 18-19; the comparison of the performance parameters of the same air quantity working point is shown in table 4.
TABLE 4 Table 4
Under the working condition of the same air quantity, compared with a comparison model machine III, the static pressure of the embodiment III is improved by 28.5Pa, and the static pressure efficiency is improved by 1.14%.
Therefore, the improvement scheme of the invention mainly improves the arc line section at the outer end of the blade to a series of local micro-step-shaped bending arcs under the condition that the main sizes of the impeller, the air inlet and the ventilator are not changed, so that the boundary layer separation and the sustainable development deterioration are restrained to a certain extent, the reduction of the area of a main air flow channel and the larger loss caused by the boundary layer separation are reduced, the working capacity and the working efficiency of the impeller are improved to a certain extent, the performance and the efficiency of the ventilator are improved, the energy consumption and the noise are reduced, and the positive significance is realized.
The foregoing has shown and described the basic principles, principal features and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, and that the above embodiments and descriptions are merely illustrative of the principles of the present invention, and various changes and modifications may be made without departing from the spirit and scope of the invention, which is defined in the appended claims.
Claims (6)
1. The design method of the impeller comprising the local step-shaped blades is characterized in that the impeller comprises a plurality of uniformly distributed arc-shaped backward blades, the diameters of the inlet and outlet of the blades are phi D1 and phi D2 respectively, the endpoints of a blade bus are a point c and a point a, and the wrap angle of the blades is phi;
the width of a runner inlet of an adjacent blade is W, W is the minimum distance from a point c to a non-working surface of the adjacent blade, the minimum distance corresponds to a point c 'of the non-working surface of the adjacent blade, and the intersection point of a cc' extension line and the working surface of the adjacent blade is a point c '';
the design method comprises the following steps:
1) Taking the connecting line of the point c' and the center of the impeller as a radius to form a first circle, wherein the diameter of the first circle is phi D W The method comprises the steps of carrying out a first treatment on the surface of the Taking the center of the impeller as a round point, and the diameter of the round point along the arc line of the blade is smaller than phi D W Is an inner arc, greater than phi D W The part of the arc line is an outer end arc line;
2) Selecting diameter phi D n ，ΦD n =（1.015～1.045）×ΦD w ；
3) Diameter phi D along the radial direction of the impeller n And phi D 2 The outer end arc line of the blade between the blades is divided into n sections of arc lines;
4) The center of the impeller is taken as a rotation center, the n arc lines are respectively rotated outwards at a certain rotation angle, and adjacent arc lines obtained after rotation are sequentially connected, so that a series of steps are formed on the surface of the blade;
wherein the working surface of the blade comprises a smooth section and a bench section; the step section is close to the outer edge of the blade; the step section comprises n continuous steps which gradually bulge towards the rotation direction of the impeller; the inlet and outlet of the blade working face arc line respectively correspond to the point c and the point a of the blade bus, and the step section is positioned at the diameter phi D n And phi D 2 Between them.
2. According to claimThe method of designing an impeller including partially stepped blades as claimed in claim 1, wherein the blade is characterized by a diameter ΦD on the blade bus n The corresponding point is a n The dividing mode of the n-section arc lines is as follows: d (D) i =D 2 -(D 2 -D n ) X i/n, where i= [1, n]，n=[3,20]From diameter phiD 2 To phi D n The intersection points of each concentric circle and the blade bus are as follows in sequence: a, a 1 ,…，a i ,…，a (n-1) ,a n I.e. from point a to point a on the blade outer end bus n The bus segments of the dots are divided into: aa 1 ,a 1 a 2 ,…，a (i-1) a i ，…，a (n-1) a n N segments in total.
3. The method of designing an impeller including partial stepped vanes of claim 2, wherein aa 1 ,a 1 a 2 ,…，a (i-1) a i ，…，a (n-1) a n Respectively rotates to a new position aa 1 Rotated to bb 1 ，a 1 a 2 Rotated to c 1 b 2 ,…，a (i-1) a i Rotated to c (i-1) b i ，…，a (n-1) a n Rotated to c (n-1) b n ；a (n-1) a n The rotation angle of the segment is theta n =θ，a (n-2) a (n-1) The rotation angle of the segment is theta (n-1) =2×θ，…，a (i-1) a i The rotation angle of the segment is theta i = (n-i+1) ×θ，…， a 1 a 2 The rotation angle of the segment is theta 2 = (n-1)×θ，aa 1 The rotation angle of the segment is theta 1 =n×θ; through the respective rotation of the arcs, the wrap angle phi of the blade is reduced to phi 1 ，φ 1 =φ-n×θ。
4. The method for designing an impeller including partial stepped blades according to claim 3, wherein adjacent arc segments obtained after rotation are sequentially connected in the following manner: straight line connectionc i Point and b i Point, i= [1, n-1]Passing through the middle point e i Line segment c i b i Is a perpendicular f to i g i And arc line section c (i-1) b i Intersecting at f i And arc line section c i b (i+1) Intersecting at g i In e i The point is taken as the center, and the straight line f i g i Rotated by an angle gamma in the opposite direction to the direction of rotation of the impeller, wherein gamma= [5 °,40 ]]With blade arc segment c (i-1) b i Intersecting at u i With blade arc segment c i b (i+1) Intersecting at v i Thereby forming u 1 v 1 ，u 2 v 2 ，…，u i v i ，…，u n- 1 v n-1 N-1 partial steps are formed, and the straight lines are connected with a n Point and b n Dots and steps u are formed in the same manner n v n 。
5. The method of designing an impeller including partially stepped blades according to claim 4, wherein the compound camber line "bu" includes n partially stepped shapes 1 v 1 u 2 v 2 …u i v i …u n v n c' is used as the cambered surface molded line of the working surface of the blade.
6. The method of designing an impeller including partial stepped blades according to claim 5, wherein θ= [0.05 °,0.25 ° ].
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110339895.1A CN113027815B (en) | 2021-03-30 | 2021-03-30 | Impeller comprising partial stepped blades and design method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110339895.1A CN113027815B (en) | 2021-03-30 | 2021-03-30 | Impeller comprising partial stepped blades and design method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113027815A CN113027815A (en) | 2021-06-25 |
| CN113027815B true CN113027815B (en) | 2023-05-30 |
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Family Cites Families (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3027845A (en) * | 1959-11-16 | 1962-04-03 | Worthington Corp | Impeller tip pocket |
| GB2032048A (en) * | 1978-07-15 | 1980-04-30 | English Electric Co Ltd | Boundary layer control device |
| JP2884562B1 (en) * | 1998-04-14 | 1999-04-19 | 木村工機株式会社 | Centrifugal blower impeller |
| JP4020104B2 (en) * | 2004-06-22 | 2007-12-12 | 松下電器産業株式会社 | Multi-wing fan |
| KR100802022B1 (en) * | 2006-11-03 | 2008-02-12 | 삼성전자주식회사 | Turbofan |
| JP2010174852A (en) * | 2009-02-02 | 2010-08-12 | Daikin Ind Ltd | Cross flow fan and air conditioner with the same |
| JP5353864B2 (en) * | 2010-11-18 | 2013-11-27 | パナソニック株式会社 | Blower |
| JP2012241684A (en) * | 2011-05-24 | 2012-12-10 | Mitsubishi Electric Corp | Axial fan |
| CN214742327U (en) * | 2021-03-30 | 2021-11-16 | 浙江科贸智能机电股份有限公司 | Impeller comprising partially stepped blades |
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| CN113027815A (en) | 2021-06-25 |
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